In a test experiment on a model aeroplane in a wind tunnel, the flow speeds on the upper and lower surfaces of the wing are `70ms^(-1)` and `83ms^(-1)` respectively. What is the lift on the wing, if its area is `2.5m^(2)`? Take the density of air to be `1.3kgm^(-3)`

Explanation

To find the lift on the wing of the model aeroplane, we will use Bernoulli's principle and the formula for lift based on pressure difference. Here are the steps to solve the problem:

### Step 1: Identify the given values
- Velocity on the upper surface of the wing, \( V_1 = 70 \, \text{m/s} \)
- Velocity on the lower surface of the wing, \( V_2 = 83 \, \text{m/s} \)
- Area of the wing, \( A = 2.5 \, \text{m}^2 \)
- Density of air, \( \rho = 1.3 \, \text{kg/m}^3 \)

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